Thermal barrier coating on a surface

ABSTRACT

A thermal barrier coating, or TBC ( 26 ), and method for forming the TBC ( 26 ). The TBC ( 26 ) is formed of a thermal-insulating material that contains yttria-stabilized zirconia (YSZ) alloyed with at least a third oxide. The TBC ( 26 ) is formed to also contain elemental carbon, and may potentially contain carbides and/or a carbon-containing gas that forms from the thermal decomposition of carbon. The TBC ( 26 ) is characterized by lower density and thermal conductivity, high temperature stability and improved mechanical properties. To exhibit the desired effect, the third oxide is more particularly one that increases the lattice strain energy of the TBC microstructure as a result of having an ion size that is sufficiently different than a zirconium ion.

BACKGROUND OF INVENTION

1. Field of the Invention

This invention relates to thermal-insulating coatings for componentsexposed to high temperatures, such as the hostile thermal environment ofa gas turbine engine. More particularly, this invention is directed to athermal barrier coating (TBC) containing elemental carbon and/orcarbides in yttria-stabilized zirconia that has been alloyed with atleast a third oxide to increase the lattice strain energy of the TBCgrains. The resulting TBC is characterized by lower density and thermalconductivity, high temperature stability, and improved mechanicalproperties from a hardening effect between carbon and the third oxide.

2. Description of the Related Art

Higher operating temperatures for gas turbine engines are continuouslysought in order to increase their efficiency. However, as operatingtemperatures increase, the high temperature durability of the componentswithin the hot gas path of the engine must correspondingly increase.Significant advances in high temperature capabilities have been achievedthrough the formulation of nickel and cobalt-base superalloys.Nonetheless, when used to form components of the turbine, combustor andaugmentor sections of a gas turbine engine, such alloys alone are oftensusceptible to damage by oxidation and hot corrosion attack, and as aresult may not retain adequate mechanical properties. For this reason,these components are often protected by a thermal barrier coating (TBC)system. TBC systems typically include an environmentally-protective bondcoat and a thermal-insulating topcoat, typically referred to as the TBC.Bond coat materials widely used in TBC systems includeoxidation-resistant overlay coatings such as MCrAlX (where M is iron,cobalt and/or nickel, and X is yttrium or another rare earth or reactiveelement), and oxidation-resistant diffusion coatings such as diffusionaluminides that contain nickel-aluminum (NiAl) intermetallics.

TBC materials are typically ceramic materials and particularly zirconia(ZrO₂) that is partially or fully stabilized by yttria (Y₂O₃), magnesia(MgO), ceria (CeO₂), calcia (CaO), scandia (Sc₂O₃) or other oxides.Binary yttria-stabilized zirconia (YSZ) is widely used as a TBC materialbecause of its high temperature capability, low thermal conductivity anderosion resistance in comparison to zirconia stabilized by other oxides,e.g., ceria-stabilized zirconia, which exhibits poorer erosionresistance as a result of being relatively soft. YSZ is also preferredas a result of the relative ease with which it can be deposited byplasma spraying, flame spraying and physical vapor deposition (PVD)techniques. In plasma spraying processes, the coating material istypically in the form of a powder that is melted by a plasma as itleaves a spray gun. As a result, a plasma-sprayed TBC is formed by abuildup of molten “splats” and has a microstructure characterized byirregular flattened grains and a degree of inhomogeneity and porosity.TBC's employed in the highest temperature regions of gas turbine enginesare often deposited by electron beam physical vapor deposition (EBPVD),which yields a columnar, strain-tolerant grain structure that is able toexpand and contract without causing damaging stresses that lead tospallation. Similar columnar microstructures can be produced using otheratomic and molecular vapor processes, such as sputtering (e.g., high andlow pressure, standard or collimated plume), ion plasma deposition, andall forms of melting and evaporation deposition processes (e.g.,cathodic arc, laser melting, etc.).

In order for a TBC to remain effective throughout the planned life cycleof the component it protects, it is important that the TBC has andmaintains a low thermal conductivity throughout the life of thecomponent, including during high temperature excursions. However, thethermal conductivities of TBC materials such as YSZ are known toincrease over time when subjected to the operating environment of a gasturbine engine. As a result, TBC's for gas turbine engine components areoften deposited to a greater thickness than would otherwise benecessary. Alternatively, internally cooled components such as bladesand nozzles must be designed to have higher cooling flow. Both of thesesolutions are undesirable for reasons relating to cost, component lifeand engine efficiency. As a result, it can be appreciated that furtherimprovements in TBC technology are desirable, particularly as TBC's areemployed to thermally insulate components intended for more demandingengine designs.

U.S. Pat. No. 5,906,895 to Hamada et al. discloses a method ofinhibiting the deterioration of the thermal properties of a TBC bysuppressing a reaction sintering mechanism said to occur in TBC's athigh temperatures. In Hamada et al., a high temperature compound (suchas a carbide, nitride or another high temperature material) is said tobe compounded into a YSZ TBC deposited by a plasma spraying process.According to three plasma spraying techniques disclosed by Hamada etal., the high temperature compound appears to be present as splatsdispersed within the TBC as a result of the plasma spraying process.According to a fourth technique disclosed by Hamada et al., aplasma-sprayed TBC is infiltrated with a feed gas of the hightemperature compound, apparently forming a coating of the compound onthe inter-splat boundaries of the porous TBC. Following this treatment,any remaining feed gas would inherently escape the TBC through the samepassages that allowed the gas to infiltrate the TBC. With each approach,the high temperature compound is said to suppress reaction sintering ofthe YSZ TBC by some unexplained mechanism.

In commonly-assigned U.S. Pat. No. 6,492,038 to Rigney et al., a morethermally-stable TBC is achieved by inhibiting grain growth(coarsening), sintering, and pore redistribution (the coalescence orcoarsening of smaller pores to form larger pores) during hightemperature excursions. According to Rigney et al., resistance to heattransfer through a TBC is determined in part by the amount ofmicrostructural defects within the grains of the TBC. Rigney et al.teach that such defects can be created by composition-induced defectreactions and process-induced porosity, the former of which includesvacancies that result from the need in ionic solids to maintain chargeneutrality, as is the case in YSZ where substitution of zirconia (ZrO₂)with yttria (Y₂O₃) in the lattice yields a vacancy. On the other hand,process-induced porosity includes pore formation that occurs duringcoating as a component is rotated relative to the deposition source. Aprimary example is the “sunrise-sunset” vapor-surface mechanisms thatoccur during rotation of a component during deposition of TBC from avapor cloud, such as by PVD, the result of which is a textured growth ofthe deposit in which pores are formed between columns, within thecolumns, and between secondary growth arms contained within the columns.

Rigney et al. teach a technique by which process-induced porosity in aTBC is preserved by incorporating extremely fine precipitates into theTBC microstructure. More particularly, Rigney et al. teach that limitedamounts of extremely fine carbide and/or nitride precipitates formed atthe defects, pores and grain boundaries of the TBC microstructure serveto pin the TBC grain boundaries to inhibit sintering, grain coarsening,and pore redistribution during high temperature excursions, with theeffect that the microstructure, and consequently the thermalconductivity of the TBC, is stabilized. Rigney et al. teach thatsuitable carbiding/nitriding techniques include depositing the TBC usinga physical vapor deposition technique in an atmosphere that containscarbon and/or nitrogen vapors, gases or compounds, and/or heat-treatingin the presence of a gas containing carbon and/or nitrogen gases orcompounds. Contrary to Hamada et al., the carbide/nitride precipitatesmust be incorporated as extremely fine precipitates in order to pin theTBC grain boundaries.

While the incorporation of carbide/nitride precipitates in accordancewith Rigney et al. makes possible a more stabilized TBC microstructures,further improvements in TBC microstructure and processes would bedesirable.

SUMMARY OF INVENTION

The present invention generally provides a thermal barrier coating (TBC)and method for forming the coating on a component intended for use in ahostile environment, such as the superalloy turbine, combustor andaugmentor components of a gas turbine engine. The method of thisinvention is particularly directed to producing a TBC characterized bylower density and thermal conductivity, high temperature stability, andimproved mechanical properties. Improvements obtained by this inventionare particularly evident with TBC having a columnar grain structure,such as those deposited by EBPVD and other PVD techniques, though theinvention is also applicable to TBC deposited by such methods as plasmaspraying.

The invention generally entails a TBC formed of a thermal-insulatingmaterial that contains yttria-stabilized zirconia (YSZ) alloyed with atleast a third oxide. The TBC is formed to also contain elemental carbon,and may potentially contain carbides and/or a carbon-containing gas thatforms from the thermal decomposition of carbon. According to theinvention, the TBC is characterized by lower density and thermalconductivity, high temperature stability and improved mechanicalproperties. To exhibit the desired effect, the third oxide is moreparticularly one that increases the lattice strain energy of the TBCmicrostructure as a result of having an ion size that is sufficientlydifferent from a zirconium ion (Zr⁴⁺). While not wishing to be held toany particular theory, increased strain energies are believed to act asscattering sites for lattice vibrations (phonons) that contribute to thethermal conductivity of YSZ. It is believed that metal oxides having anabsolute percent ion size difference relative to zirconium ions of atleast that of the yttrium anion (Y³⁺), i.e., at least 13 percent, areeffective to produce significant strains due to ionic size. Oxides ofmetals such as cerium, gadolinium, neodymium, lanthanum, dysprosium,tantalum, magnesium, calcium, strontium and barium meet thisrequirement, a particular example being ceria (CeO₂) which has anabsolute percent ion size difference relative to zirconium ions of about30 percent. However, ceria additions to YSZ are known to have theundesirable effect of increasing coating density and reducing erosionresistance. In the present invention, it has been unexpectedly shownthat a ceria-modified YSZ coating that is further modified by dopingwith carbon undergoes hardening during thermal aging as an apparentresult of a reaction that occurs between ceria and the elemental carbonpresent in the TBC. Advantageously, density of the coating is alsodecreased due to the carbon content forming small and stable pores whenthe coating is sufficiently heated.

Other objects and advantages of this invention will be betterappreciated from the following detailed description.

BRIEF DESCRIPTION OF DRAWINGS

FIG. 1 is a perspective view of a high pressure turbine blade.

FIG. 2 schematically represents a cross-sectional view of the blade ofFIG. 1 along line 2—2, and shows a thermal barrier coating system on theblade in accordance with the invention.

FIGS. 3 and 4 are graphs comparing the thermal conductivities anddensities, respectively, of thermal barrier coatings formed inaccordance with the prior art and the present invention.

DETAILED DESCRIPTION

The present invention is generally applicable to components subjected tohigh temperatures, and particularly to components such as the high andlow pressure turbine nozzles and blades, shrouds, combustor liners andaugmentor hardware of gas turbine engines. An example of a high pressureturbine blade 10 is shown in FIG. 1. The blade 10 generally includes anairfoil 12 against which hot combustion gases are directed duringoperation of the gas turbine engine, and whose surface is thereforesubjected to hot combustion gases as well as attack by oxidation,corrosion and erosion. The airfoil 12 is protected from its hostileoperating environment by a thermal barrier coating (TBC) systemschematically depicted in FIG. 2. The airfoil 12 is anchored to aturbine disk (not shown) with a dovetail 14 formed on a root section 16of the blade 10. Cooling passages 18 are present in the airfoil 12through which bleed air is forced to transfer heat from the blade 10.While the advantages of this invention will be described with referenceto the high pressure turbine blade 10 shown in FIG. 1, the teachings ofthis invention are generally applicable to any component on which athermal barrier coating may be used to protect the component from a hightemperature environment.

The TBC system 20 is represented in FIG. 2 as including a metallic bondcoat 24 that overlies the surface of a substrate 22, the latter of whichis typically a superalloy and the base material of the blade 10. As istypical with TBC systems for components of gas turbine engines, the bondcoat 24 is preferably an aluminum-rich composition, such as an overlaycoating of an MCrAlX alloy or a diffusion coating such as a diffusionaluminide or a diffusion platinum aluminide of a type known in the art.Aluminum-rich bond coats of this type develop an aluminum oxide(alumina) scale 28, which is grown by oxidation of the bond coat 24. Thealumina scale 28 chemically bonds a TBC 26, formed of athermal-insulating material, to the bond coat 24 and substrate 22. TheTBC 26 of FIG. 2 is represented as having a strain-tolerantmicrostructure of columnar grains 30. As known in the art, such columnarmicrostructures can be achieved by depositing the TBC 26 using aphysical vapor deposition technique, such as EBPVD. While much of thefollowing discussion will focus on columnar TBC of the type representedby FIG. 2, the invention is also believed to be applicable tononcolumnar TBC deposited by such methods as plasma spraying, includingair plasma spraying (APS). A TBC of this type is in the form of molten“splats,” resulting in a microstructure characterized by irregularflattened grains and a degree of inhomogeneity and porosity.

As with prior art TBC's, the TBC 26 of this invention is intended to bedeposited to a thickness that is sufficient to provide the requiredthermal protection for the underlying substrate 22 and blade 10,generally on the order of about 75 to about 300 micrometers. As a resultof the processes by which the TBC 26 is deposited, the individual grains30 of the TBC 26 are characterized by microstructural defects and pores32 within the grains 30 and at and between the grain boundaries. Thedefects and pores 32 are believed to decrease the thermal conductivityof a TBC grain 30, and therefore the TBC 26 as a whole. The TBC 26 ofthe present invention is provided with reduced thermal conductivity as aresult of its composition.

According to the invention, the thermal-insulating material of the TBC26 is based on binary yttria-stabilized zirconia (YSZ), but alloyed tocontain at least a third metal oxide. The thermal-insulating materialpreferably contains about 4 to about 8 weight percent yttria, thoughlesser or greater amounts of yttria could be used. According to oneaspect of the invention, the third oxide has an absolute percent ionsize difference relative to zirconium ions of at least that of anyttrium anion (Y³⁺), i.e., at least 13 percent, so as to producesignificant strains due to ionic size. According to a second aspect ofthe invention, the thermal-insulating material of the TBC 26 is furthermodified to contain elemental carbon in the form of precipitateclusters, from which may evolve a carbon-containing gas (e.g., carbonmonoxide (CO) and/or carbon dioxide (CO₂)) as a result of thermaldecomposition of carbon. In combination, the presence of elementalcarbon clusters and the above-specified third metal oxide has been shownto reduce the density and thermal conductivity of a YSZ TBC.

The third metal oxide is preferably ceria (CeO₂), which has an absolutepercent ion size difference relative to zirconium ions of about 30percent. However, it is believed that other or additional oxides thatmeet the ion size requirement of this invention could be used, examplesof which are gadolinium oxide (Gd₂O₃), neodymia (Nd₂O₃), lanthana(La₂O₃), dysprosia (Dy₂O₃), tantala (Ta₂O₅). magnesia (MgO), calcia(CaO), strontia (SrO) and barium oxide (BaO). A notable exception to theion size requirement is ytterbia (Yb₂O₃), which has an ion sizedifference of 9%, but appears to have a sufficiently high ionic mass toachieve similar reductions in thermal conductivity when combined withelemental carbon in YSZ. Based on an investigation discussed below,ceria in amounts of about 10 to about 20 weight percent of thethermal-insulating material is believed to have the beneficial effect ofincreasing lattice strain energy to the extent that thermal conductivityof the TBC 26 is reduced by about 10%. It is foreseeable that higherlevels of ceria could be used, e.g., up to about thirty weight percent,though with the disadvantage of increasing density of the TBC 26. It isalso foreseeable that lower levels of ceria could be used, e.g., aslittle as about one weight percent, but with a corresponding reducedeffect on thermal conductivity. The increased strain energy caused byion size difference of the third oxide is believed to act as scatteringsites for lattice vibrations (phonons), which contribute to the thermalconductivity of YSZ. It is therefore believed that those metal oxidesnoted above as producing high strains due to ionic size would also beeffective if present in sufficient amounts. These oxides are summarizedin Table I below with their absolute percent ion size differencerelative to zirconium ions.

TABLE I Oxide % Ion Size Difference MgO 16 CaO −25 SrO −42 BaO −70 La₂O₃−34 CeO₂ −30 Nd₂O₃ −27 Gd₂O₃ 19 Dy₂O₃ −15 Yb₂O3 −9 Ta₂O5 −13

Magnesia, calcia, strontia and barium oxide are alkaline-earth metaloxides, while lanthana, ceria, neodymia, gadolinium oxide, dysprosia andytterbia are rare-earth metal oxides. While alkaline-earth metal oxidesand rare-earth metal oxides have been used in the past to stabilizezirconia, the present invention makes use of these oxides in combinationwith elemental carbon for reasons discussed below.

A first beneficial effect of elemental carbon is believed to be throughan increase in the amount of porosity within the TBC 26 during thecoating operation, and then a stabilization of the porosity and even anincrease in porosity during subsequent high temperature excursions as aresult of the carbon thermally decomposing to yield thecarbon-containing gas. Such an effect is particularly important if thethird oxide is heavier than yttria (e.g., ceria at about 7.65 g/cc vs.yttria at about 4.84 g/cc) and therefore may have the effect ofincreasing the density and weight of the TBC 26.

If the third oxide is ceria, the presence of elemental carbon in the TBC26 has been determined to provide the additional benefit of hardeningthe TBC 26. In particular, ceria-stabilized zirconia is known to haverelatively poor erosion resistance as a result of ceria being relativelysoft (e.g., a microhardness of 1.8 to 2.4 GPa versus 4.4 to 4.6 GPa forYSZ). The deposition and/or presence of carbon in the TBC 26 has beenshown provide for a reaction with ceria at elevated temperatures thatyields precipitates of carbides and oxycarbides (e.g., ZrO_(x)C_(y)),producing a hardening effect. The hardening effect is believed to occurduring deposition of the TBC 26 at temperatures of about 900° C. toabout 1000° C. under appropriate conditions, or during a post-depositionthermal aging treatment in the same temperature range. While not wishingto be held to any particular theory, a reaction between carbon and ceriais believed to occur as a result of ceria vapor being highly reactivewith carbon vapor, both of which exist if the TBC 26 is deposited byPVD, such as EBPVD. The reactivity of ceria with carbon is significantlygreater than that of zirconia with carbon (discussed in greater detailbelow), and therefore provides a mechanism by which carbon in the formof carbides can be co-deposited or subsequently evolved. If this theoryis correct, one or more of the oxides listed above as increasing latticestrain energy may also react with carbon for the same reason, therebybenefitting from a similar hardening effect.

A preferred method for co-depositing carbon and the thermal-insulatingmaterial of the TBC 26 is by the simultaneous evaporation of a suitablesource of carbon and YSZ alloyed with ceria, which may be combined in asingle ingot or provided in separate ingots. An example of a suitablecarbon source is graphite, though carbon in the form of a compound couldalso be used, such as zirconium carbide (ZrC), titanium carbide (TiC),tantalum carbide (TaC), and molybdenum carbide (Mo₂C). The desirableadded porosity discussed previously is believed to be the result of ashadowing effect that occurs when two insoluble phases are deposited byEBPVD. More particularly, “primary” porosity is believed to be createdsurrounding deposited elemental carbon clusters (and possibly clustersof carbides, oxycarbides, etc., all of which are insoluble in YSZ)during EBPVD as a result of zirconia vapor flux being blocked from theimmediate vicinity of the second phase clusters. Another benefit ofco-deposition of carbon clusters (and possibly carbide clusters) byEBPVD has been observed to be the formation of many additionalinterfaces associated with sub-grain boundaries, possibly due to whatappears to be related to the presence of carbon promoting the nucleationof new sub-grains and inhibiting diffusion processes of grain growth.The result is a continuous nucleation of new grains, which produces afine sub-grained TBC structure with numerous interfaces that reducethermal conductivity through the TBC grains. Open porosity levelsobserved within TBC deposited in accordance with this invention are wellin excess of YSZ TBC deposited from an identical YSZ source material(minus the carbon source) under identical conditions. While YSZ TBC istypically deposited by EBPVD to have open porosity levels of not morethan about 15 to 20 volume percent, open porosity levels on the order ofabout 30 volume percent are believed to be possible with the presentinvention, with typical open porosity levels being about 30 to about 35volume percent.

Fine “secondary” porosity occurs with this invention as a result ofelemental carbon (and possibly carbides) reacting with oxygen to formcarbon monoxide and/or another carbon-containing gas (e.g., carbondioxide) during high temperature excursions (e.g., above about 950° C.).As a result of the primary porosity surrounding the deposited carbon,there is sufficient pore volume for carbon-containing gases to evolveand produce very fine pores (“micropores”) within the TBC 26. As thesegases form and some of the original primary porosity is lost as a resultof shrinkage of smaller pores and growth of larger pores at the expenseof smaller pores (pore coarsening and redistribution) during sintering,some of the gases are entrapped within the micropores. The entrappedgases are believed to counteract surface tension energies that are thedriving force for the shrinkage of small pores during sintering.Therefore, in addition to reducing the density and thermal conductivityof the TBC 26, the added fine porosity made possible with this inventionis thermally stable, i.e., less susceptible to shrinkage.

Additional porosity may also be generated in part through one or both ofthe following reactions:

ZrO₂+3C=ZrC+2CO

ZrO₂+2C=Zr+2CO

These reactions have been reported in the art as occurring within atemperature range of about 900° C. to about 1200° C. if a sufficientlylow vacuum of about 10⁻⁴ to 10⁻⁵ Torr (about 1.33×10⁻⁴ to 1.33×10⁻⁵mbar) is maintained (because the equilibrium pressure of carbon monoxideis very low, e.g., about 10⁻⁴ Torr at 870° C.). According to thistheory, zirconium and zirconium carbide would form during deposition byEBPVD under these conditions, and primary porosity would also formaround these particles as a result of the shadowing effect during theEBPVD process. During subsequent heating, gaseous carbon monoxide wouldthen form, resulting in new secondary porosity within the TBC 26 and itsgrains 30, as well as carbon monoxide (and/or carbon dioxide or anothercarbon-containing gas) entrapped within micropores that are remnants ofthe original primary porosity (i.e., pores 32). Carbides (e.g., ZrC) andoxycarbides are also potential byproducts of the above reactions, andmay serve to stabilize the micropore structure of the TBC 26 byanchoring and pinning the grain boundaries and pores 32 of the TBC 26.

While the above discussion is directed to columnar TBC of the typerepresented by FIG. 2, the benefits of the invention may also beachieved with noncolumnar TBC, as when deposited by such methods asplasma spraying. As previously discussed, a plasma-sprayed TBC isdeposited as molten “splats” that produces a grain structurecharacterized by irregular flattened grains surrounded by inhomogeneousporosity. With the present invention, an effective amount of porositycan be maintained to stabilize the TBC microstructure during hightemperature excursions by co-depositing a powder of YSZ alloyed withceria along with a powder of elemental carbon or carbon-based compounds.An example is by simultaneously spraying graphite and YSZ powders orspraying a graphite-coated YSZ powder. A carbon-containing gas wouldthen be evolved and some of the existing open porosity closed during asubsequent thermal treatment that is sufficient to partially sinter theTBC. The process and result differ from that of U.S. Pat. No. 5,906,895to Hamada et al., in that Hamada et al. teach forming a plasma-sprayedTBC that either contains splats of carbides or another high temperaturecompound, or is infiltrated with a feed gas to form a coating ofcarbides (or another high temperature compound) on the inter-splatboundaries of the TBC. Neither of these TBC”s could contain entrappedgas because of the open porous nature of the plasma-sprayed TBC.

In an investigation leading to this invention, TBC's were deposited byEBPVD on specimens formed of the superalloy Ren é N5 on which a platinumaluminide (PtAl) bond coat had been deposited. Some of the specimenswere coated by evaporating an ingot of 7% YSZ (zirconia stabilized byabout 7 wt. % yttria) to deposit a conventional 7% YSZ TBC. Otherspecimens were coated by evaporating an ingot of 7% YSZ alloyed withabout 16 weight percent ceria (7% YSZ+ceria). Finally, additionalspecimens were coated by co-evaporating separate ingots of graphite andeither the 7% YSZ or the 7% YSZ+ceria material (the resulting materialsof which are referred to below as 7% YSZ+C and 7% YSZ+C+ceria,respectively). The graphite ingots included a tungsten cap which, duringEBPVD, forms a molten surface pool through which carbon evaporates inaccordance with U.S. Pat. No. 5,296,274 to Movchan et al. Similar toEBPVD processes of the past, the specimens were loaded into a coatingchamber so as to be supported above the ingot(s), and the chamberevacuated to achieve a partial vacuum of about 4.7×10⁻⁴ to about6.6×10⁻⁴ Torr (about 6.3×10⁻⁴ to about 8.8×10⁻⁴ mbar). The specimenswere then heated to a temperature of between about 900° C. and 1000° C.,and then coated while being rotated at a rate of about 25 rpm. The 7%YSZ and 7% YSZ+ceria ingots were evaporated using electron beam gunsoperated at a power level of about 19.5 kW. When co-evaporatinggraphite, a second electron beam gun operated at a power level of about23 kW was used to project a separate electron beam onto the graphiteingot. The TBC's were deposited to have thicknesses on the order ofabout 150 micrometers. The 7% YSZ+ceria and 7% YSZ+C+ceria coatingscontained about 16 weight percent ceria, while each of the coatingsproduced by co-evaporating graphite (7% YSZ+C and 7% YSZ+C+ceria)contained a dispersion of carbon (solid graphite) and possibly zirconiumcarbide, which congregated at the defects, pores and sub-grains(interfaces within the grains) of the YSZ microstructure during growthof the individual grains. Following coating, all of the specimensunderwent aging in air at about 1200° C. for about two hours.

The thermal conductivities and densities for all of the specimens aresummarized in the graphs of FIGS. 3 and 4, in which the ranges, standarddeviations and averages are plotted. The thermal conductivities for thebaseline 7% YSZ, 7% YSZ+ceria, 7% YSZ+C and 7% YSZ+C+ceria specimenswere measured at about 890° C., and are tabulated in Table II below. Thevalues for “% difference” are based on the average conductivities of the7% YSZ+ceria, 7% YSZ+C and 7% YSZ+C+ceria specimens relative to thebaseline 7% YSZ specimens.

TABLE II Specimen Avg. (W/mK) Std. Dev. % Difference 7% YSZ 22 0.17 − 7%YSZ + ceria 1.85 0.11 −14.0 7% YSZ + C 18 0.13 −13.0 7% YSZ + C + ceria1.6 0.07 −25.0

The results from this investigation strongly evidenced the individualand combined effects that carbon and ceria additions have on theporosity and thermal conductivity of a YSZ TBC, as well as the effectthat carbon has on YSZ alloyed with ceria. The reduced thermalconductivities of the specimens containing elemental carbon wereattributed to an increase in porosity observed in the as-depositedcondition as well as additional porosity that developed following agingat 1200° C. The reduced thermal conductivities of the specimenscontaining ceria were attributed to the increased lattice strain energyresulting from ceria having an ion size which is 30 percent smaller thanzirconium ions (Zr⁴⁺), causing an increase in lattice strain energy ofthe TBC grains. Surprisingly, the combination of both carbon and ceriaprovided the greatest reduction in density, from an average of about4.73 g/cm³ for 7% YSZ to as low as about 4.38 g/cm³ for 7% YSZ+C+ceria.

Finally, microhardness measurements before and after the aging stepshowed that the 7% YSZ specimens had hardnesses of about 6 GPa beforeand after aging, and the 7% YSZ+ceria specimens had hardnesses of about4 GPa before and after aging. In contrast, hardness increased from about2.8-3 GPa to about 5.8-6 GPa for the 7% YSZ+C+ceria specimens,evidencing that a reaction had occurred to considerably increase thehardnesses of the 7% YSZ+C+ceria specimens. Such results indicate thatthe manner in which carbon and YSZ alloyed with ceria were co-depositedand aged produced a ternary system of carbides and oxycarbides, and notsimply a mixture of carbon, ceria and YSZ. In any event, the resultingmaterial exhibited a hardness comparable to that of YSZ, indicating thatequivalent erosion resistance could be expected. Such improvedmechanical properties in combination with a thermal conductivity ofabout 25% less than YSZ evidenced a thermal-insulating material that issuitable as a TBC in the hostile environment within gas turbine engines.

While the invention has been described in terms of a preferredembodiment, it is apparent that other forms could be adopted by oneskilled in the art. For example, instead of depositing the TBC by EBPVD,other atomic and molecular vapor deposition processes could be used,such as sputtering, ion plasma deposition, and all forms of melting andevaporation deposition processes. Accordingly, the scope of theinvention is to be limited only by the following claims.

What is claimed is:
 1. A thermal barrier coating on a surface of acomponent, the thermal barrier coating comprising a thermal-insulatingmaterial of yttria-stabilized zirconia alloyed with at least a thirdoxide having an absolute percent ion size difference relative to azirconium ion of at least 13 percent, the third oxide being present inthe thermal-insulating material in an amount sufficient to increaselattice strain energy of grains of the thermal barrier coating, thethermal barrier coating containing elemental carbon, carbides,oxycarbides and/or a carbon-containing gas.
 2. A thermal barrier coatingaccording to claim 1, wherein the third oxide is selected from the groupconsisting of ceria, magnesia, calcia, strontia, barium oxide, lanthana,neodymia, gadolinium oxide, dysprosia, ytterbia and tantala.
 3. Athermal barrier coating according to claim 2, wherein thethermal-insulating material is alloyed with an additional oxide selectedfrom the group consisting of ceria, magnesia, calcia, strontia, bariumoxide, lanthana, neodymia, gadolinium oxide, dysprosia, ytterbia andtantala.
 4. A thermal barrier coating according to claim 1, wherein thethird oxide is ceria.
 5. A thermal barrier coating according to claim 4,wherein the thermal-insulating material contains about 10 to about 20weight percent ceria, the balance essentially zirconia stabilized byabout 4 to about 8 yttria.
 6. A thermal barrier coating according toclaim 1, wherein the elemental carbon, carbides, oxycarbides and/orcarbon-containing gas are within pores that are within grains and at andbetween grain boundaries of the thermal-insulating material.
 7. Athermal barrier coating according to claim 6, wherein at least some ofthe pores contain elemental carbon.
 8. A thermal barrier coatingaccording to claim 6, wherein at least some of the pores entrap thecarbon-containing gas.
 9. A thermal barrier coating according to claim8, wherein the carbon-containing gas is at least one gas chosen from thegroup consisting of carbon monoxide and carbon dioxide.
 10. A thermalbarrier coating according to claim 6, wherein at least some of the porescontain the elemental carbon, at least some of the pores containcarbides or oxycarbides, and at least some of the pores entrap thecarbon-containing gas.
 11. A thermal barrier coating according to claim1, wherein the microstructure of the thermal barrier coating consists ofcolumnar grains so that the microstructure is columnar, or flattenedgrains so that the microstructure is noncolumnar and inhomogeneous. 12.A thermal barrier coating on a surface of a superalloy component, thethermal barrier coating comprising: a bond coat on the component; athermal-insulating material of yttria-stabilized zirconia alloyed withabout 10 to about 20 weight percent ceria, the thermal insulatingmaterial having a columnar microstructure with pores and sub-graininterfaces within, at and between grain boundaries of themicrostructure, at least some of the pores containing elemental carbon,carbides, oxycarbides, and/or a carbon-containing gas.
 13. A thermalbarrier coating according to claim 12, wherein at least some of thepores contain the elemental carbon, at least some of the pores containcarbides or oxycarbides, and at least some of the pores entrap thecarbon-containing gas.
 14. A thermal barrier coating according to claim12, wherein the thermal-insulating material comprises a ternary reactionproduct of ceria and the elemental carbon.
 15. A thermal barrier coatingaccording to claim 14, wherein the ternary reaction product comprisescarbides and/or oxycarbides.